Aircraft Spoiler Actuator Using Aerodynamic Deployment
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Solution Overview
Problem
Aircraft spoilers face challenges in rapid deployment due to the need for substantial load and power capacity, which increases the size and weight of actuators, potentially eroding aerodynamic benefits and requiring significant on-board space, especially when encountering short-duration wind gusts.
Innovation Solution
The design employs a hinged top flap spoiler that deploys quickly using negative air pressure, with a smaller and less powerful actuator that retracts the spoiler, leveraging aerodynamic forces to reduce deployment time and actuator size, and features a linear guide mechanism and clutch arrangement for efficient movement between stowed and deployed configurations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a large actuator with substantial load and power capacity is used to deploy the spoiler quickly, then the deployment speed is improved, but the weight and size of the actuator increases
Solution Approach 1:
The patent uses aerodynamic lift force generated by the wing during flight to counteract the weight and deployment resistance of the spoiler. The spoiler is designed to be pushed upward by the aerodynamic forces acting on the wing surface, eliminating the need for a heavy actuator to overcome gravity and inertial resistance during deployment.
Solution Approach 2:
The spoiler deployment system utilizes the aerodynamic forces already present during aircraft flight to automatically deploy the spoiler. The actuator only needs to release the locking mechanism, and the aerodynamic forces do the work of deploying the spoiler, making the system self-actuating during flight conditions.
2Speed
If a large actuator with substantial power capacity is used to deploy the spoiler quickly, then the deployment speed is improved, but the complexity of the actuator system increases
Solution Approach 1:
The aerodynamic lift force acts as a counterbalancing force that simplifies the actuator design. Instead of requiring a complex high-power actuator to push the spoiler against aerodynamic resistance, the system uses the aerodynamic force itself to do the work, reducing the actuator to a simple release mechanism.
Solution Approach 2:
The system uses the aerodynamic environment during flight to automatically deploy the spoiler. The actuator only needs to release the latching mechanism, and the spoiler deploys under the influence of aerodynamic forces, eliminating the need for complex power transmission systems.
3Speed
If a large actuator is used to deploy the spoiler quickly, then the deployment speed is improved, but the on-board space required increases
Solution Approach 1:
By using aerodynamic forces to counteract the deployment resistance, the actuator size is dramatically reduced. The actuator only needs to accommodate a release mechanism rather than a large motor or hydraulic system, significantly reducing the volume occupied by the actuator system.
Solution Approach 2:
The aerodynamic forces during flight serve to deploy the spoiler automatically, eliminating the need for large power sources. This reduces the actuator to a compact release mechanism that occupies minimal space within the wing structure.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution allows for rapid deployment of the spoiler in less than a second, effectively reacting to gusts and reducing structural deformations, enabling a lighter airframe and improved dynamic flight performance while minimizing weight penalties.
Implementation Method 1
Movement of the hinged top flap into the second position may result from negative pressure at the upper surface of the aircraft wing. During flight, a negative pressure exists on the upper surface of the wing. This negative pressure causes an upward lifting force which urges the hinged top flap into the second position.
Data Source
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AI summary
The invention provides an aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration. The spoiler comprises an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.